GB1009314A - By-pass gas turbine engines - Google Patents
By-pass gas turbine enginesInfo
- Publication number
- GB1009314A GB1009314A GB33005/64A GB3300564A GB1009314A GB 1009314 A GB1009314 A GB 1009314A GB 33005/64 A GB33005/64 A GB 33005/64A GB 3300564 A GB3300564 A GB 3300564A GB 1009314 A GB1009314 A GB 1009314A
- Authority
- GB
- United Kingdom
- Prior art keywords
- section
- duct
- pass
- openings
- gas turbine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 239000007789 gas Substances 0.000 abstract 5
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/38—Introducing air inside the jet
- F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Incineration Of Waste (AREA)
Abstract
1,009,314. Gas turbine jet engines. GENERAL MOTORS CORPORATION. Aug. 13, 1964 [Sept. 10, 1963], No. 33005/64. Heading F1J. A gas turbine jet engine of the by-pass type comprises at the entry of the by-pass duct into the exhaust pipe, an exhaust pipe section with circumferentially-spaced openings, and a chutering co-axially disposed within the exhaust pipe and having radially-inwardly-extending chutes which promote mixing of the by-pass air and exhaust gas flows. The shoot ring is movable axially with respect to the exhaust pipe so as to throttle the by-pass air flow by variably obstructing the chutes. The invention is described with reference to a two-spool type engine, the turbine exhaust passage being indicated at 22 and the downstream end of the by-pass air duct at 31 in Fig. 2, the turbine exhaust passage being defined by sections 26 and 27 which are interconnected by a section 35, while the by-pass duct is defined by an outer wall 10. The section 35 is formed with a number of openings 41 through which by-pass air flows to mix with the turbine exhaust gases in the duct 22, there being ten such openings in the present embodiment. The section 35 is also formed with a frustoconical portion 37 which co-operates with the downstream end of the wall 10, a piston ring element 38 carried by the portion 37 engaging with the cylindrical surface 39 of the wall 10 to provide a seal. An axially-movable member 45 is disposed within the duct section 35, the member being formed with chutes 46 each of which co-operates with an opening 41 in the section 35 so as to guide the inflowing by-pass air. The member 45 is shown in its forward position in full lines and in its rearward position in which it restricts the flow area of the openings 41 in chain-dotted lines. The member 45 carries pairs of rollers 55 which engage within channel section members 53 which extend longitudinally of the duct section 35. The member 45 also carries a pair of brackets 58 which are connected by links 66 to the rods 65 of hydraulic or other actuators 57 whereby the axial position of the chute member may be controlled. The engine may alternatively be a gas turbine propeller engine.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US307904A US3273345A (en) | 1963-09-10 | 1963-09-10 | Gas turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1009314A true GB1009314A (en) | 1965-11-10 |
Family
ID=23191668
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB33005/64A Expired GB1009314A (en) | 1963-09-10 | 1964-08-13 | By-pass gas turbine engines |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US3273345A (en) |
| GB (1) | GB1009314A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2313565A1 (en) * | 1975-06-02 | 1976-12-31 | Gen Electric | GAS TURBINE ENGINE WITH ADJUSTABLE BY-PASS AND PROCESS FOR CONTROL OF THIS ENGINE |
| GB2161862A (en) * | 1983-05-27 | 1986-01-22 | Pierre Giraud | Double flow turbine engine equipped with a thrust reverser |
| US20140053563A1 (en) * | 2012-08-27 | 2014-02-27 | Snecma | Method for assembling a nozzle and an exhaust case of a turbomachine |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5706651A (en) * | 1995-08-29 | 1998-01-13 | Burbank Aeronautical Corporation Ii | Turbofan engine with reduced noise |
| GB0603285D0 (en) * | 2006-02-18 | 2006-03-29 | Rolls Royce Plc | A gas turbine engine |
| RU2490496C2 (en) * | 2011-11-10 | 2013-08-20 | Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") | Outlet device of double-flow gas-turbine engine |
| US20160017815A1 (en) * | 2013-03-12 | 2016-01-21 | United Technologies Corporation | Expanding shell flow control device |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB871016A (en) * | 1957-06-12 | 1961-06-21 | Power Jets Res & Dev Ltd | Gas turbine jet propulsion engines |
| US3060680A (en) * | 1957-12-30 | 1962-10-30 | Rolls Royce | By-pass gas-turbine engine and control therefor |
| DE1148817B (en) * | 1959-06-23 | 1963-05-16 | Rolls Royce | Twin-flow gas turbine jet engine |
| US3115748A (en) * | 1960-05-06 | 1963-12-31 | Rolls Royce | Gas turbine engine |
| FR79090E (en) * | 1960-07-11 | 1962-10-19 | Nord Aviation | Combined turbojet-ramjet |
| GB910178A (en) * | 1960-08-02 | 1962-11-14 | Rolls Royce | Gas turbine by-pass jet engine |
| FR1306025A (en) * | 1961-08-08 | 1962-10-13 | Snecma | Variable blocking coefficient mixer in double-flow mixed-flow reactors |
-
1963
- 1963-09-10 US US307904A patent/US3273345A/en not_active Expired - Lifetime
-
1964
- 1964-08-13 GB GB33005/64A patent/GB1009314A/en not_active Expired
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2313565A1 (en) * | 1975-06-02 | 1976-12-31 | Gen Electric | GAS TURBINE ENGINE WITH ADJUSTABLE BY-PASS AND PROCESS FOR CONTROL OF THIS ENGINE |
| GB2161862A (en) * | 1983-05-27 | 1986-01-22 | Pierre Giraud | Double flow turbine engine equipped with a thrust reverser |
| US20140053563A1 (en) * | 2012-08-27 | 2014-02-27 | Snecma | Method for assembling a nozzle and an exhaust case of a turbomachine |
| GB2508260A (en) * | 2012-08-27 | 2014-05-28 | Snecma | Assembling an exhaust system of a turbomachine |
| US9399952B2 (en) * | 2012-08-27 | 2016-07-26 | Snecma | Method for assembling a nozzle and an exhaust case of a turbomachine |
| GB2508260B (en) * | 2012-08-27 | 2019-11-06 | Snecma | A method for assembling a nozzle and an exhaust case of a turbomachine |
Also Published As
| Publication number | Publication date |
|---|---|
| US3273345A (en) | 1966-09-20 |
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